CN108516109B - Umbrella-shaped space debris or micro-fluidic star protection device for spacecraft - Google Patents
Umbrella-shaped space debris or micro-fluidic star protection device for spacecraft Download PDFInfo
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- CN108516109B CN108516109B CN201810272904.8A CN201810272904A CN108516109B CN 108516109 B CN108516109 B CN 108516109B CN 201810272904 A CN201810272904 A CN 201810272904A CN 108516109 B CN108516109 B CN 108516109B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/56—Protection against meteoroids or space debris
Abstract
The invention discloses an umbrella-type space debris or micro-fluidic star protection device for a spacecraft, which comprises an umbrella-type protection cover, a telescopic spring and a controllable hinge, wherein the umbrella-type protection cover is of an umbrella-shaped structure formed by tightly splicing a plurality of triangular protection panels, the inner side of each panel is connected with a controllable sliding barrel arranged on a main supporting rod in a sliding manner through a side supporting rod, and the umbrella-type protection cover can change the inclination direction of the protection cover along the sliding of the controllable sliding barrel on the main supporting rod along with the impact of space debris or micro-fluidic stars so as to reduce the impact damage. The invention greatly reduces the direct force of the space debris on the protective cover, increases the buffer time of the protective cover on the space debris, improves the protective capability on the space debris, and improves the protective capability by more than 40 times to the maximum.
Description
Technical Field
The invention belongs to the technical field of space debris and micro-fluidic star environment protection, and particularly relates to an umbrella-shaped space debris or micro-fluidic star protection device for a spacecraft.
Background
The space debris, also called space garbage, is the waste left in space by human aerospace activities and is the main pollution source of space environment. Since the first satellite was launched in 1957, the total number of space debris has exceeded 4 million, the total mass has reached several million kilograms, the average number of space debris observed by ground telescopes and radars has increased by about 200 per year, and the number of space debris greater than 10 centimeters has now exceeded 9200. Space debris is mainly distributed in low orbit regions below 2000 km, and they pose a serious threat to space vehicles in the near-earth space.
The size range of the space debris comprises micron-sized, millimeter-sized, centimeter-sized and even meter-sized space debris, wherein the space debris of centimeter-sized and above mainly comprises upper-level space debris, spacecraft at the end of a mission, objects abandoned during working, unexpected disintegration debris, aluminum oxide residues, sodium potassium particles and the like; the millimeter-scale space debris mainly comprises spacecraft surface spalling debris, spatters, aluminum oxide residues, sodium potassium particles, micro-fluid bodies, unexpected disintegration debris and the like; the micron-sized space debris mainly comprises spalling debris, sputtering materials, aluminum oxide dust, micro-fluid and the like.
Space debris larger than 10cm can cause destructive damage to the spacecraft, and the orbit can be measured through a foundation telescope or a radar at present, so that the damage can be effectively prevented by adopting a pre-warning evasive strategy; centimeter-level space debris can also cause the spacecraft to be thoroughly damaged, at present, no feasible protective measures exist, and the only method is to try to reduce the risk of fatal damage to the astronauts and the spacecraft in the design and operation of the spacecraft; millimeter-scale space debris can cause the surface of the spacecraft to generate collision pits and even perforate the bulkhead, the collision positions are different, and the damage degree can be greatly different. Wherein table 1 lists the basic information of the space fraction.
Table 1 basic information of space debris
Mainly taking monitoring and evading measures for large space debris with the size larger than 10 cm; mainly taking protective measures for small space fragments below 1 cm; and the protection of the space plain film with the size exceeding 1cm brings the increase of the weight and causes the sharp rise of the cost. On the near-earth orbit, the speed of space debris is thousands of meters per second, and when the space debris collides with a spacecraft, the relative speed can reach more than 10km/s, so that the risk is great.
Micro-fluidic stars refer to solid particles that originate in comets and small planetary ribbons and move in interplanetary space. The microfluid star may collide with the spacecraft and cause damage to the spacecraft, the type and extent of which depends on the size, configuration, operating time of the spacecraft and the properties of the microfluid star such as mass, density, velocity, etc. Such impact damage includes rupture of the pressure vessel, degradation of the porthole, delamination of the thermal control coating, reduction of thermal protection, and damage to the antenna system.
At present, aiming at a space debris and micro-fluidic star protection method, a spacecraft adopts different measures to avoid the ultra-high speed collision of the space debris and the micro-fluidic star, for the space debris with the size of more than 10cm, the space debris has large kinetic energy and can be destructively damaged when colliding with the spacecraft, however, most of the debris can be tracked and observed by ground observation equipment, and therefore, the spacecraft is avoided by adopting an active avoidance mode; for space debris with the size less than 1cm, the space debris has small kinetic energy and cannot usually generate destructive damage when impacting a spacecraft, so the spacecraft is protected by adopting a passive protection method. For debris between 1-10cm, the spacecraft has no effective protection due to its large kinetic energy and is not observable, and therefore the debris becomes dangerous debris.
At present, the Whipple protective structure is mainly used for protecting space debris, namely, a buffer plate is arranged in front of a cabin wall of a spacecraft to crush, even melt and vaporize incident projectiles to form debris clouds, so that point load of space debris collision is changed into surface load, the strength of impact load is reduced, and damage to the cabin wall of the spacecraft is reduced. This form of construction is referred to as a Whipple guard structure, see FIG. 1.
But with the rapid deterioration of space debris environment, the problem of insufficient protection capability gradually emerges. People have developed multiple structures based on Whipple protective structure, and these structures can be divided into according to the number of layers of buffering screen: single buffering screen protective structure, two buffering screen protective structure and many buffering screen protective structure. Compared with Whipple protection structures, the protection capability of the protection structures is greatly improved, and therefore the protection structures are also called enhanced protection structures. The single-layer screen reinforced protective structure and the multi-layer protective structure are exemplified below.
The single-layer screen enhanced protection structure comprises a cellular board sandwich plate structure and a foamed aluminum protection structure. The front panel is equivalent to a buffer screen in the Whipple protective structure, and the rear panel is equivalent to a rear wall in the Whipple protective structure. Honeycomb panels can be classified into aluminum panel honeycomb panel structures and carbon fiber honeycomb panel structures according to the difference of panels (see document i.w.members.vers ion 4.0 of the IADC protection Manual [ R ]. Germany, 2009.).
The multilayer impact protection structure (MS compares with Whipple protection structure, the multilayer impact protection structure increases the number of buffer screens (generally 3-5 layers), as shown in figure 2. the increase of the number of buffer screens ensures that when the projectile impacts the protection structure, the multilayer buffer screens can intercept the projectile layer by layer, ensure that the projectile can be broken fully, even melted and vaporized, and change a large amount of kinetic energy into internal energy.
Subsequently, astronauts have proposed a density gradient type protective structure as shown in fig. 3. A density gradient material is a material that exhibits an increasing or decreasing wave impedance through its thickness. The density gradient type protection structure consists of a layer of density gradient buffer screen, a protection space and a rear wall. The density gradient buffer screen is a composite screen which is manufactured according to the wave impedance decreasing rule in the impact direction. The novel space debris protective structure is different from the conventional enhanced protective structure.
However, these materials or structures are designed to allow for frontal impingement of space debris and are often directed to single space debris or micrometeors. If the device is installed on a spacecraft in a large area, the weight of the spacecraft can be greatly increased, and the device can only be fixed on the spacecraft.
Disclosure of Invention
The invention aims to provide an umbrella-shaped space debris or micro-fluidic star protection device for a spacecraft, which is placed in front of the spacecraft to be protected, greatly reduces the impact strength of the space debris by utilizing the principle that the protection device is inclined relative to the incident direction of the space debris, and can further reduce the impact damage of the space debris by utilizing the high-speed rotation of the protection device.
An umbrella-shaped space debris or micro-fluidic star protection device for a spacecraft comprises an umbrella-shaped protection cover, a telescopic spring and a controllable hinge which is fixed on the spacecraft to realize the direction change of the umbrella-shaped protection cover, the umbrella-shaped protective cover is of an umbrella-shaped structure formed by tightly splicing a plurality of triangular protective panels, the inner side of each protective panel is connected with a controllable sliding barrel arranged on a main supporting rod in a sliding mode through a linking piece and a side supporting rod meshed with the linking piece, the vertex of each triangular protective panel is connected to a first sliding barrel in a sharing mode, the main supporting rod penetrates through the first sliding barrel and fixes the first sliding barrel on the top end of the main supporting rod through a telescopic spring, the tail end of the main supporting rod is fixedly connected with the controllable hinge, and the umbrella-shaped protective cover can change the inclination direction of the protective cover along the sliding of the controllable sliding barrel on the main supporting rod along with the impact of space fragments or micro-planets, so that the impact damage is reduced.
Wherein, the telescopic spring is an extension spring.
An umbrella-type space debris or micrometeor protection device for a spacecraft comprises an umbrella-type protection cover, a telescopic spring and a controllable hinge fixed on the spacecraft for realizing the direction change of the umbrella-type protection cover, wherein the umbrella-type protection cover is tightly spliced into an umbrella-shaped structure by a plurality of triangular protection panels, the inner side of each protection panel is connected with a controllable slide cylinder arranged on a main support rod in a sliding way through a linking piece and a side support rod meshed with the linking piece, the vertexes of the triangular protection panels are connected to the slide cylinder I in common, the main support rod passes through the slide cylinder I and a main shaft of the controllable slide cylinder, the controllable slide cylinder is fixed on the tail end of the main support rod through the telescopic spring, the tail end of the main support rod is fixedly connected with the controllable hinge, the umbrella-type protection cover can change the inclination direction of the protection cover along the sliding way of the controllable slide cylinder on the main support rod along with the impact of the space debris or the microm, and impact damage is reduced.
Wherein, the telescopic spring is a high compression spring.
Wherein the number of triangular protective panels is greater than 12.
Wherein the link is a hinge structure.
The protective cover is made of single materials or composite materials of aluminum alloy, titanium alloy, Nextel ceramic or Kevlar fibers.
Wherein the protective cover panel is a density gradient type space debris protective panel.
Wherein, the inclination angle of the umbrella-shaped protective cover is realized by the back and forth movement of the controllable sliding cylinder.
The space debris protection device can greatly reduce the direct force of the space debris on the protection cover, increase the buffer time of the protection cover on the space debris, and further improve the safety performance of the protection cover on the space debrisHigh protection against space debris to
The protection cover of inclination is for example, and its protective capacities improves 4 times, if increase spring structure or elastic material as the buffering, protective capacities improves more than 40 times.
Drawings
FIG. 1 is a schematic diagram of a Whipple protective structure of the prior art;
FIG. 2 is a schematic view of a prior art multi-layer impact protection structure;
FIG. 3 is a schematic view of a density gradient type space debris guard structure;
fig. 4 is a schematic structural diagram of an umbrella-type shield used in the umbrella-type space debris or micro-fluidic star device for spacecraft of the present invention. (ii) a
FIG. 5 is a schematic structural view of an umbrella-type space debris or micro-fluidic star shield for a spacecraft in accordance with an embodiment of the present invention;
wherein: 1. a protective cover; 2. a link; 3. a side support bar; 4. a controllable slide cylinder; 5. a main support bar; 6. a retractable spring; 7. and a first sliding cylinder.
FIG. 6 is a schematic structural view of an umbrella-type space debris or micro-fluidic star shield for a spacecraft in accordance with another embodiment of the present invention;
wherein: 1. a protective cover; 2. a link; 3. a side support bar; 4. a controllable slide cylinder; 5. a main support bar; 6. a retractable spring; 7. and a first sliding cylinder.
Fig. 7 is a schematic view showing the force and velocity decomposition of the umbrella-type space debris or the micro-fluidic star protector for spacecraft according to the present invention when the umbrella-type space debris or the micro-fluidic star protector receives the impact of the space debris.
Detailed Description
The present invention will be described in further detail with reference to the attached drawings, which are only illustrative and not intended to limit the scope of the present invention in any way. The invention is further described with reference to the following figures.
The core of the invention is to utilize a large-area protective cover with a controllable inclination angle and a telescopic spring, reduce the acting force vertically acting on the protective cover by reducing the inclination angle, and increase the buffering time and the buffering distance by utilizing the telescopic spring, thereby realizing the purposes of decelerating and protecting space debris.
Referring to fig. 1, fig. 1 shows a schematic diagram of a typical Whipple structure mentioned in the present invention. As can be seen in fig. 1, the conventional whisple guard structure is a single layer of sheet metal (a typical material is shown here as an aluminum alloy). The space debris (equivalent to a collision "projectile") first strikes the protective structure layer and then is likely to strike the spacecraft (here, the collision "rear wall").
Referring to fig. 2, fig. 2 shows a schematic view of a prior art multi-layer impact protection structure. As can be seen from fig. 2, compared with the single-layer protection structure, the multi-layer protection structure is formed by a plurality of protection layers to form a protection array. Space debris (equivalent to a collision "projectile") is likely to strike the spacecraft (here the "rear wall" of the collision) only after passing through the multi-layer shield structure (i.e., the multi-layer shield).
Referring to fig. 3, fig. 3 shows a schematic diagram of a density gradient type space debris guard structure. As can be seen from fig. 3, instead of the conventional single protective layer, a density gradient structure is used, in which the density of the material varies in a gradient manner with the thickness, which is equivalent to the superposition of multiple layers of homogeneous density materials. The space debris (corresponding to a collision "projectile") first strikes the density gradient structure (here the density gradient screen) before it can strike the spacecraft (here the collision "back wall").
Referring to fig. 4, fig. 4 shows a schematic structural view of an umbrella-type shield in the umbrella-type space debris or micro-fluidic star protecting device for spacecraft of the present invention. As can be seen from the figure, the tiltable protective cover of the invention is in an umbrella-shaped structure, the protective cover is in an umbrella shape after being opened, and the tilting angle of the umbrella is adjustable. The umbrella-shaped protective cover consists of 12 triangular protective panels, and each protective panel is connected with a controllable sliding cylinder on the main supporting rod through a side supporting rod.
Referring to fig. 5, fig. 5 shows the structure of the protection device in a specific embodiment of the present invention, wherein the protection device in one of the specific embodiments comprises an umbrella-shaped aluminum alloy protection cover 1, a retractable spring 6, and a controllable hinge (not shown) fixed on the spacecraft to realize the direction change of the umbrella-shaped protection cover, wherein the umbrella-shaped protection cover is tightly spliced into an umbrella-shaped structure by a plurality of triangular protection panels, the inner side of each protection panel is connected with a controllable slide cylinder 4 arranged on a main support rod 5 in a sliding way through a link 2 of the hinge and a side support rod 3 engaged with the link, the vertex of each triangular protection panel is connected to the slide cylinder 7 in common, the main support rod passes through the slide cylinder 7 and fixes the slide cylinder 7 on the top end of the main support rod 5 through the retractable spring 6, the end of the main support rod 5 is fixedly connected with the controllable hinge, along with the impact of space debris or micro-stars, the umbrella-shaped protective cover can change the inclination direction of the protective cover 1 by sliding the controllable slide cylinder on the main support rod 5, so that the impact damage is reduced. In this embodiment, the retractable spring is a pull-up spring.
Referring to fig. 6, fig. 6 shows the structure of the protective device in another embodiment of the present invention, wherein the star-like protective device of this embodiment comprises an umbrella-shaped protective cover 1, a retractable spring 6, and a controllable hinge fixed on the spacecraft for changing the direction of the umbrella-shaped protective cover, wherein the umbrella-shaped protective cover 1 is tightly spliced into an umbrella-shaped structure by a plurality of triangular protective panels, the inner side of each protective panel is connected with a controllable slide cylinder 4 slidably arranged on a main support rod 5 through a link 2 of the hinge and a side support rod 3 engaged with the link, the vertex of each triangular protective panel is commonly connected to the slide cylinder 7, the main support rod 5 passes through the main shafts of the slide cylinder 7 and the controllable slide cylinder 4, and the controllable slide cylinder 4 is fixed on the end of the main support rod 5 through the retractable spring 6, the end of the main support rod 5 is fixedly connected with the controllable hinge, along with the impact of space debris or micro-stars, the umbrella-shaped protective cover can change the inclination direction of the protective cover by sliding on the main supporting rod along the controllable sliding cylinder, so that the impact damage is reduced. In this embodiment, the retractable spring is a high compression spring.
In the two embodiments, the inclination angle of the umbrella protection cover can be realized by the forward and backward movement of the controllable sliding cylinder.
When a space debris having a mass m and a sectional area s hits the shield at a velocity V, assuming that the thickness of the shield is d, the average impact strength P of the shield material when the shield is not penetrated is calculated by the following formula.
P×s×d＝0.5×m×(Vs inθ)2
Then there are:
P＝0.5×m×(Vs inθ)2/s/d
therefore, as the shield inclination angle θ is smaller, the impact strength to which the shield material is subjected is smaller. When theta is
Due to
The protection capability is increased by a factor of 4 compared to a normal incidence shield.
Typically, the thickness of the shield material is 0.1-0.3 cm.
Referring to fig. 7, the spring's extension or compression length d and ultimate stress F are determined by the mass and velocity of the space debris to be protected. See the following equation:
F×d＝0.5×m×V2
for a space debris with a mass of 1g, when the velocity is 10km/s, as can be seen from the above formula, F × d is 5 × 104J。
In the absence of a spring, the damping distance of the protective cover is at most the thickness of the protective cover, typically in the order of 0.1cm, and assuming that the damping distance of the spring is at least 1cm, the damping distance of the protective cover can be increased by at least 10 times, and thus its impact resistance is increased by at least 10 times.
Thirdly, the tail end of the umbrella is fixed on the spacecraft by using a controllable hinge, and the direction of the protective cover can be changed by the controllable hinge. The controllable hinge may utilize gearing or the like to effect a change in orientation of the guard.
Therefore, the protection cover has a certain inclination angle relative to the impact direction of the space debris, and the protection capacity of resisting the impact of the space debris can be improved by more than 40 times by combining the spring buffer device.
Although particular embodiments of the invention have been described and illustrated in detail, it should be understood that various equivalent changes and modifications can be made to the above-described embodiments according to the inventive concept, and that it is intended to cover such modifications as would come within the spirit of the appended claims and their equivalents.
Claims (9)
1. An umbrella-shaped space debris or micro-fluidic star protection device for a spacecraft comprises an umbrella-shaped protection cover, a telescopic spring and a controllable hinge fixed on the spacecraft for realizing the direction change of the umbrella-shaped protective cover, the umbrella-shaped protective cover is of an umbrella-shaped structure formed by tightly splicing a plurality of triangular protective panels, the inner side of each protective panel is connected with a controllable sliding barrel arranged on a main supporting rod in a sliding mode through a linking piece and a side supporting rod meshed with the linking piece, the vertex of each triangular protective panel is connected to a first sliding barrel in a sharing mode, the main supporting rod penetrates through the first sliding barrel and fixes the first sliding barrel on the top end of the main supporting rod through a telescopic spring, the tail end of the main supporting rod is fixedly connected with the controllable hinge, and the umbrella-shaped protective cover can change the inclination direction of the protective cover along the sliding of the controllable sliding barrel on the main supporting rod along with the impact of space fragments or micro-planets, so that the impact damage is reduced.
2. The umbrella-type space debris or micro-fluidic star protector of claim 1, wherein the retractable spring is an extension spring.
3. An umbrella-type space debris or micrometeor protection device for a spacecraft comprises an umbrella-type protection cover, a telescopic spring and a controllable hinge fixed on the spacecraft for realizing the direction change of the umbrella-type protection cover, wherein the umbrella-type protection cover is tightly spliced into an umbrella-shaped structure by a plurality of triangular protection panels, the inner side of each protection panel is connected with a controllable slide cylinder arranged on a main support rod in a sliding way through a linking piece and a side support rod meshed with the linking piece, the vertexes of the triangular protection panels are connected to the slide cylinder I in common, the main support rod passes through the slide cylinder I and a main shaft of the controllable slide cylinder, the controllable slide cylinder is fixed on the tail end of the main support rod through the telescopic spring, the tail end of the main support rod is fixedly connected with the controllable hinge, the umbrella-type protection cover can change the inclination direction of the protection cover along the sliding way of the controllable slide cylinder on the main support rod along with the impact of the space debris or the microm, and impact damage is reduced.
4. An umbrella-type space debris or micro-fluidic star protector as claimed in claim 3, wherein the retractable spring is a high compression spring.
5. An umbrella-type space debris or micro-fluidic star device according to claim 1 or 3, wherein the number of triangular guard panels is greater than 12.
6. An umbrella space debris or micro-fluidic star device according to claim 1 or 3 wherein the link is a hinge structure.
7. An umbrella-type space debris or micro-fluidic star device according to claim 1 or 3 wherein the shield is made of a single material or composite of an aluminium alloy, a titanium alloy, Nextel ceramic or Kevlar fibre.
8. An umbrella-type space debris or micro-fluidic star device of claim 1 or 3 wherein the protective cover panel is a density gradient space debris protective panel.
9. An umbrella space debris or micro-fluidic star device according to claim 1 or 3 wherein the degree of tilt of the umbrella shield is controlled by the forward and backward movement of the controllable shuttle.
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| CN112478199B (en) * | 2020-11-27 | 2022-06-14 | 南京航空航天大学 | Satellite flexible repeatable folding and unfolding defense device for resisting physical impact |
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| JP5505829B2 (en) * | 2009-06-12 | 2014-05-28 | 啓佑 小澤 | Space debris reduction device |
| GB2475926B (en) * | 2009-12-07 | 2011-10-19 | Phs Space Ltd | Debris impact mitigation apparatus for spacecraft |
| CN102514737B (en) * | 2011-11-08 | 2014-04-23 | 西安交通大学 | Lightweight filled composite protective structure for space debris |
| CN103072705B (en) * | 2013-01-29 | 2015-03-18 | 北京空间飞行器总体设计部 | Device for preventing condensable volatile material from entering satellite sensor |
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